Journal articles: 'Aerospace Engineering - Propulsion'

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Isikveren, A. T., A. Seitz, J. Bijewitz, A. Mirzoyan, A. Isyanov, R. Grenon, O. Atinault, J. L. Godard, and S. Stückl. "Distributed propulsion and ultra-high by-pass rotor study at aircraft level." Aeronautical Journal 119, no. 1221 (November 2015): 1327–76. http://dx.doi.org/10.1017/s0001924000011295.

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AbstractThis technical article discusses design and integration associated with distributed propulsion as a means of providing motive power with significantly reduced emissions and external noise for future aircraft concepts. The technical work reflects activities performed within a European Commission funded Framework 7 project entitled Distributed Propulsion and Ultra-high By-Pass Rotor Study at Aircraft Level, or, DisPURSAL. In this instance, the approach of distributed propulsion includes a Distributed Multiple-Fans Concept driven by a limited number of engine cores as well as one unique solution that integrates the fuselage with a single propulsor (dubbed Propulsive-Fuselage Concept) – both targeting entry-in-service year 2035+. Compared to a state-of-the-art, year 2000 reference aircraft, designs with tighter coupling between airframe aerodynamics and motive power system performance for medium-to-long-range operations indicated potentially a 40-45% reduction in CO2-emissions. An evolutionary, year 2035, conventional morphology gas-turbine aircraft was predicted to be –33% in CO2-emissions.

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Perry, Aaron T., Phillip J. Ansell, and Michael F. Kerho. "Aero-Propulsive and Propulsor Cross-Coupling Effects on a Distributed Propulsion System." Journal of Aircraft 55, no. 6 (November 2018): 2414–26. http://dx.doi.org/10.2514/1.c034861.

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Gray, Justin S., and Joaquim R. R. A. Martins. "Coupled aeropropulsive design optimisation of a boundary-layer ingestion propulsor." Aeronautical Journal 123, no. 1259 (October 31, 2018): 121–37. http://dx.doi.org/10.1017/aer.2018.120.

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AbstractAirframe–propulsion integration concepts that use boundary-layer ingestion (BLI) have the potential to reduce aircraft fuel burn. One concept that has been recently explored is NASA’s STARC-ABL aircraft configuration, which offers the potential for fuel burn reduction by using a turboelectric propulsion system with an aft-mounted electrically driven BLI propulsor. So far, attempts to quantify this potential fuel burn reduction have not considered the full coupling between the aerodynamic and propulsive performance. To address the need for a more careful quantification of the aeropropulsive benefit of the STARC-ABL concept, we run a series of design optimisations based on a fully coupled aeropropulsive model. A 1D thermodynamic cycle analysis is coupled to a Reynolds-averaged Navier–Stokes simulation to model the aft propulsor at a cruise condition and the effects variation in propulsor design on overall performance. A series of design optimisation studies are performed to minimise the required cruise power, assuming different relative sizes of the BLI propulsor. The design variables consist of the fan pressure ratio, static pressure at the fan face, and 311 variables that control the shape of both the nacelle and the fuselage. The power required by the BLI propulsor is compared with a podded configuration. The results show that the BLI configuration offers 6–9% reduction in required power at cruise, depending on assumptions made about the efficiency of power transmission system between the under-wing engines and the aft propulsor. Additionally, the results indicate that the power transmission efficiency directly affects the relative size of the under-wing engines and the aft propulsor. This design optimisation, based on computational fluid dynamics, is shown to be essential to evaluate current BLI concepts and provides a powerful tool for the design of future concepts.

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Bore, C. L. "Some contributions to propulsion theory — Fuel consumption formulae and general range equation." Aeronautical Journal 97, no. 963 (March 1993): 118–20. http://dx.doi.org/10.1017/s0001924000025203.

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The permanent urgency of aircraft design during the author’s career at Hawker Aircraft, a.k.a. British Aerospace Kingston, inhibited publication of his advances of theory. So he collected those on propulsion and presented them to the Royal Aeronautical Society in a lecture “Some Unpublished Contributions to Propulsion Theory” on 11 March 1992. The meeting proposed that the material should be published in full, and F. W. Armstrong helpfully suggested that the best way for future reference would be to divide the material into Technical Notes on related topics, each capable of standing alone. These have been reworked to stand separately, as follows:1)Fuel consumption formulae and the general range equation2)The Stream Force Theorem and applications to propulsion3)Non-isentropic duct flow and the general wake traverse4)Propulsion streamtubes in supersonic flow and the first supercritical intake cowl5)Rotary jet thrust augmenters(a)fallacy of Foa’s theory and correction(b)the jet fan augmenter.

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Seitz, A., D. Schmitt, and S. Donnerhack. "Emission comparison of turbofan and open rotor engines under special consideration of aircraft and mission design aspects." Aeronautical Journal 115, no. 1168 (June 2011): 351–60. http://dx.doi.org/10.1017/s000192400000587x.

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Abstract An integrated parametric model involving the design of propulsion system, airframe and flight mission is presented. Based hereon, the carbon dioxide (CO2) emission characteristics of advanced direct-drive turbofan and open rotor powered aircraft are analysed against pertinent aircraft and propulsion system design parameters. In addition, initial concept-specific trend statements on nitrogen oxides (NOx) as well as propulsor noise emission characteristics are derived. The obtained results contribute to a better understanding of more appropriate aircraft design attributes for advanced system architectures.

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Cusati, Vincenzo, Salvatore Corcione, Fabrizio Nicolosi, and Qinyin Zhang. "Improvement of Take-Off Performance for an Electric Commuter Aircraft Due to Distributed Electric Propulsion." Aerospace 10, no. 3 (March 11, 2023): 276. http://dx.doi.org/10.3390/aerospace10030276.

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The need for environmentally responsible solutions in aircraft technology is now considered the priority for global challenges related to the limited supply of traditional fuel sources and the potential global hazards associated with emissions produced by traditional aircraft propulsion systems. Several projects, including research into highly advanced subsonic aircraft concepts to drastically reduce energy or fuel usage, community noise, and emissions associated with aviation, are currently ongoing. One of the proposed propulsion concepts that address European environmental goals is distributed electric propulsion. This paper deals with the detailed aerodynamic analyses of a full-electric commuter aircraft with fuel cells, which expects two primary electric motors at the wing tip and eight other electric motors distributed along the wingspan as secondary power sources. The main objective was the numerical estimation of propulsive effects in terms of lift capabilities at take-off conditions to quantify the possible reduction of take-off field length. However, the aircraft was designed from scratch, and therefore a great effort was spent to design both propellers (for the tip and distributed electric motors) and the wing flap. In this respect, several numerical tests were performed to obtain one of the best possible flap positions. This research work estimated a reduction of about 14% of the take-off field length due to only the propulsive effects. A greater reduction of up to 27%, if compared to a reference conventional commuter aircraft, could be achieved thanks to a combined effect of distributed propulsion and a refined design of the Fowler flap. On the contrary, a significant increment of pitching moment was found due to distributed propulsion that may have a non-negligible impact on the aircraft stability, control, and trim drag.

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Ibrahim, K., S. Sampath, and D. Nalianda. "Voltage synchronisation for hybrid-electric aircraft propulsion systems." Aeronautical Journal 125, no. 1291 (July 22, 2021): 1611–30. http://dx.doi.org/10.1017/aer.2021.56.

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AbstractIncreasing demand for commercial air travel is projected to have additional environmental impact through increased emissions from fuel burn. This has necessitated the improvement of aircraft propulsion technologies and proposal of new concepts to mitigate this impact. The hybrid-electric aircraft propulsion system has been identified as a potential method to achieve this improvement. However, there are many challenges to overcome. One such challenges is the combination of electrical power sources and the best strategy to manage the power available in the propulsion system. Earlier methods reviewed did not quantify the mass and efficiency penalties incurred by each method, especially at system level. This work compares three power management approaches on the basis of feasibility, mass and efficiency. The focus is on voltage synchronisation and adaptation to the load rating. The three methods are the regulated rectification, the generator field flux variation and the buck-boost. This comparison was made using the propulsion system of the propulsive fuselage aircraft concept as the reference electrical configuration. Based on the findings, the generator field flux variation approach appeared to be the most promising, based on a balance of feasibility, mass and efficiency, for a 2.6MW system.

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James, Anthony. "The Aviation Conference of the Year!" Aerospace Testing International 2018, no. 3 (September 2018): 86–89. http://dx.doi.org/10.12968/s1478-2774(23)50121-6.

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The 4th Electric & Hybrid Aerospace Technology Symposium will bring together more than 200 engineering experts from aircraft manufacturers, propulsion suppliers, electronics and avionics suppliers, materials companies, aerospace research organizations and others involved in the electrification of aircraft.

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Bae, Yoon-Yeong, and George Emanuel. "Performance of an aerospace plane propulsion nozzle." Journal of Aircraft 28, no. 2 (February 1991): 113–22. http://dx.doi.org/10.2514/3.45999.

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Falzarano, Jeffrey. "Ship Resistance and Propulsion: Practical Estimation of Ship Propulsive Power." AIAA Journal 56, no. 10 (October 2018): 4218. http://dx.doi.org/10.2514/1.j057653.

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Figueiras, Iara, Maria Coutinho, Frederico Afonso, and Afzal Suleman. "On the Study of Thermal-Propulsive Systems for Regional Aircraft." Aerospace 10, no. 2 (January 24, 2023): 113. http://dx.doi.org/10.3390/aerospace10020113.

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Life without mobility is inconceivable. To enable this connectivity, one must find a way to progress towards a more sustainable transportation. In the aviation industry, a comprehensive understanding of greening technologies such as electrification of the propulsion system for commercial aircraft is required. A hybrid-electric propulsion concept applied to a regional aircraft is studied in the context of the FutPrInt50 project. To this end, the hybrid-electric propulsive system components are modeled, validated, and evaluated using computational and experimental data presented in the literature. The components are then assembled to construct the three powertrains for the hybrid-electric propulsion systems (Series, Parallel and Turboelectric) and parametric studies are carried out to study the influence of various battery parameters and hybridization factor. The performance results for a simple mission profile are generated. Together with a thermal management system, multi-objective optimization studies for the different architectures are then performed, with the power hybridization factor as the design variable and minimization of total mass and emissions as objective functions.

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Alulema, Victor, Esteban Valencia, Edgar Cando, Victor Hidalgo, and Dario Rodriguez. "Propulsion Sizing Correlations for Electrical and Fuel Powered Unmanned Aerial Vehicles." Aerospace 8, no. 7 (June 24, 2021): 171. http://dx.doi.org/10.3390/aerospace8070171.

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Despite the increasing demand of Unmanned Aerial Vehicles (UAVs) for a wide range of civil applications, there are few methodologies for their initial sizing. Nowadays, classical methods, mainly developed for transport aircraft, have been adapted to UAVs. However, these tools are not always suitable because they do not fully adapt to the plethora of geometrical and propulsive configurations that the UAV sector represents. Therefore, this work provides series of correlations based on off-the-shelf components for the preliminary sizing of propulsion systems for UAVs. This study encompassed electric and fuel-powered propulsion systems, considering that they are the most used in the UAV industry and are the basis of novel architectures such as hybrid propulsion. For these systems, weight correlations were derived, and, depending on data availability, correlations regarding their geometry and energy consumption are also provided. Furthermore, a flowchart for the implementation of the correlations in the UAV design procedure and two practical examples are provided to highlight their usability. To summarize, the main contribution of this work is to provide parametric tools to size rapidly the propulsion system components, which can be embedded in a UAV design and optimization framework. This research complements other correlation studies for UAVs, where the initial sizing of the vehicle is discussed. The present correlations suit multiple UAV categories ranging from micro to Medium-Altitude-Long-Endurance (MALE) UAVs.

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Zhao, Lei, Changqing Yuan, Xiaoming Li, and Jingjiu He. "Multiple Spacecraft Formation Flying Control around Artificial Equilibrium Point Using Propellantless Approach." International Journal of Aerospace Engineering 2022 (May 2, 2022): 1–26. http://dx.doi.org/10.1155/2022/8719645.

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This paper demonstrates a detailed analysis of the feasibility for compact formation system around an L2-type artificial equilibrium point by means of continuous low-thrust propulsion in the hybrid form of solar sail and Coulomb force propulsion. Firstly, in view of non-ideal solar sail, the position of L2-type artificial equilibrium point and numerical periodic orbits around L2 utilized as leader’s nominal trajectory are given. Secondly, considering the external disturbances in the deep space environment, the nonlinear dynamic model of the spacecraft formation system based on the circular restricted three-body problem (CRTBP) is derived, under the assumption that the leader covers the nominal trajectory and each follower adjusts its propulsive acceleration vector (that is, both its sail attitude and electrostatic charge) in order to track a desired relative trajectory. Thirdly, based on a new double power combination function reaching law, a fast integral terminal sliding mode control methodology (MFITSM) is ameliorated to achieve orbital tracking rapidly, which has better robustness against external disturbances and the buffeting effect during spacecraft propulsion simultaneously. To properly allocate control inputs, a novel optimal allocation scheme is designed to calculate the charge product of the spacecrafts and sail attitude angles, which can make the magnitude of the acceleration required from the Coulomb propulsion system minimum and avoid formation geometry instabilities by balancing electrostatic interaction between adjacent spacecraft. Finally, several numerical examples are conducted to validate the superiority of the proposed control algorithm.

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Zhang, Jing, Xianfa Zeng, and Lingyu Yang. "Model-based analysis of boundary layer ingestion effect on lateral-directional aerodynamics using differentiated boundary conditions." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 13 (September 14, 2016): 2452–63. http://dx.doi.org/10.1177/0954410016667148.

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The noteworthy feature of aircraft with distributed propulsion configuration is the integration of a blended-wing-body type airframe and an embedded distributed propulsion system, thus inducing the specific boundary layer ingestion effect. Different boundary layer ingestion effects on the distributed engines may generate asymmetric flow fields on the airframe surface, and then lead to the unique lateral-directional aero-propulsive close coupling. To investigate the lateral-directional aerodynamics influenced by boundary layer ingestion, a new comprehensive computational method based on the differentiated boundary conditions is proposed. This method uses a synthetic three-dimensional computational model including the airframe and multi-engine to analyze the aerodynamic characteristics, and the essential boundary conditions can be extracted from the thermodynamic distributed propulsion system model to represent the different boundary layer ingestion intensities on the left and right engines. Subsequently, detailed model-based analyses of boundary layer ingestion influences on the lateral-directional aerodynamic characteristics are conducted, and the influence regularities under different flight states are revealed. All the results demonstrate that the differentiated boundary layer ingestion intensities on distributed engines can certainly affect the roll and yaw aerodynamic performance of the distributed propulsion configuration aircraft.

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Chudoba, B., G. Coleman, L. Gonzalez, E. Haney, A. Oza, and V. Ricketts. "Orbital transfer vehicle (OTV) system sizing study for manned GEO satellite servicing." Aeronautical Journal 120, no. 1226 (April 2016): 573–99. http://dx.doi.org/10.1017/aer.2016.3.

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ABSTRACTIn an effort to quantify the feasibility of candidate space architectures for astronauts servicing Geosynchronous Earth Orbit (GEO) satellites, a conceptual assessment of architecture-concept and operations-technology combinations has been performed. The focus has been the development of a system with the capability to transfer payload to and from geostationary orbit. Two primary concepts of operations have been selected: (a) Direct insertion/re-entry (Concept of Operations 1 – CONOP 1); (b) Launch to low-earth orbit at Kennedy Space Center inclination angle with an orbital transfer to/from geostationary orbit (Concept of Operations 2 – CONOP 2). The study concludes that a capsule and de-orbit propulsion module system sized for the geostationary satellite servicing mission is feasible for a direct insertion/re-entry concept of operation CONOP 1. Vehicles sized for CONOP 2 show overall total mass savings when utilising the aero-assisted orbital transfer vehicle de-orbit propulsion module options compared to the pure propulsive baseline cases. Overall, the consideration of technical, operational and cost factors determine if either the aero-assisted orbital transfer vehicle concepts or the re-usable/expendable ascent/de-orbit propulsion modules is the preferred option.

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Padma Rao, Anyam Veera Venkata Naga Padma Rao, and Ankit Kumar Mishra. "Ancient World of Aerospace Technology: Technical Note." 1 2, no. 1 (March 1, 2023): 1–3. http://dx.doi.org/10.46632/jame/2/1/1.

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As per the great ancient Indian scripts over thousands of years back there are flying and levitating vehicles called as vimanas (e.g.: Pushpaka Vimana) with most efficient propulsion system (e.g.: mercury propulsion) and far more advanced than today’s technology which are even capable of travel from one planet to another planet. But even now also no one knows about manufacturing those Indian ancient vimanas.

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Goldin, Daniel S., Samuel L. Venneri, and Ahmed K. Noor. "A New Frontier in Engineering." Mechanical Engineering 120, no. 02 (February 1, 1998): 62–69. http://dx.doi.org/10.1115/1.1998-feb-1.

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This article highlights that an intelligent synthesis environment will dramatically change the tools and processes used to design future aerospace systems. Recent missions have achieved significant successes, but traditional-mission synthesis approaches, sequential design, and manufacturing processes are clearly inadequate to achieve these goals in the long term. Dramatic changes are needed in how missions are synthesized and in how aerospace systems are designed, produced, operated, maintained, and disposed of. The intelligent-synthesis-environment (ISE) concept being developed by NASA, the University of Virginia’s Center for Advanced Computational Technology at NASA's Langley Research Center in Hampton, and the Jet Propulsion Laboratory, Pasadena, CA, is an attempt to meet the needs and challenges of tomorrow’s aerospace systems. Researchers need to address a number of fundamental issues, including human factors, group and team dynamics, information security, and the costs and benefit of ISE facilities and tools in various categories of applications.

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Johansen, Donald. "Microwave Propulsion Ionizer." International Journal of Aerospace Innovations 3, no. 2 (June 2011): 85–92. http://dx.doi.org/10.1260/1757-2258.3.2.85.

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Seitz, Arne, Anaïs Luisa Habermann, Fabian Peter, Florian Troeltsch, Alejandro Castillo Pardo, Biagio Della Corte, Martijn van Sluis, et al. "Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion." Aerospace 8, no. 1 (January 13, 2021): 16. http://dx.doi.org/10.3390/aerospace8010016.

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Key results from the EU H2020 project CENTRELINE are presented. The research activities undertaken to demonstrate the proof of concept (technology readiness level—TRL 3) for the so-called propulsive fuselage concept (PFC) for fuselage wake-filling propulsion integration are discussed. The technology application case in the wide-body market segment is motivated. The developed performance bookkeeping scheme for fuselage boundary layer ingestion (BLI) propulsion integration is reviewed. The results of the 2D aerodynamic shape optimization for the bare PFC configuration are presented. Key findings from the high-fidelity aero-numerical simulation and aerodynamic validation testing, i.e., the overall aircraft wind tunnel and the BLI fan rig test campaigns, are discussed. The design results for the architectural concept, systems integration and electric machinery pre-design for the fuselage fan turbo-electric power train are summarized. The design and performance implications on the main power plants are analyzed. Conceptual design solutions for the mechanical and aero-structural integration of the BLI propulsive device are introduced. Key heuristics deduced for PFC conceptual aircraft design are presented. Assessments of fuel burn, NOx emissions, and noise are presented for the PFC aircraft and benchmarked against advanced conventional technology for an entry-into-service in 2035. The PFC design mission fuel benefit based on 2D optimized PFC aero-shaping is 4.7%.

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Gramatyka, Jakub, Przemysław Paszkiewicz, Damian Grabowski, Adrian Parzybut, Daria Bodych, Krzysztof Wróblewski, Paweł Surmacz, and Krzysztof Pietrzak. "Development of POLON—A Green Microsatellite Propulsion Module Utilizing 98% Hydrogen Peroxide." Aerospace 9, no. 6 (May 31, 2022): 297. http://dx.doi.org/10.3390/aerospace9060297.

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The following paper presents the key design and test activities associated with the development of POLON—a green microsatellite propulsion module using 98% Hydrogen Peroxide (HTP). POLON, which stands for “Polish Propulsion Module”, is the first step toward the development of a full, ready-to-be-commercialized satellite propulsion system at the Łukasiewicz—Institute of Aviation (Ł-IoA). The development of an entire microsatellite propulsion system within the frame of the POLON project effort is the natural milestone on the Ł-IoA green propulsion roadmap, which so far embodied research on fundamental HTP chemistry, work on elementary propulsion technologies, as well as the development of individual propulsion components. Within this article, POLON propulsion development logic is introduced first, and the major challenges associated with utilizing HTP for an orbital propulsion system are described. Consequently, the specific R&D activities aimed at mitigating the identified issues and risks are discussed. Those cover analytical as well as experimental work, including, but not limited to, HTP compatibility studies with candidate construction materials, waterhammer effect studies, HTP catalyst testing and evaluation, and propellant tank manufacturing studies. The initial results for those activities are presented and, finally, further development plans are discussed.

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Gallops, G. W., C. F. Weiss, and R. A. Carlton. "Integrated Propulsion System Requirements for Control of STOVL Aircraft." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 60–67. http://dx.doi.org/10.1115/1.2906531.

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This paper describes an evaluation of propulsion system requirements and capability for a Short Take-Off/Vertical Landing (STOVL) aircraft employing modulation of the propulsive lift distribution for pitch and roll control in hover. The effects of propulsive lift nozzle configuration and propulsion system dynamic response were evaluated using a combined system simulation consisting of a six degree of freedom aircraft model, engine model, and integrated flight/propulsion control. The response and stability of propulsive lift control are compared with control by reaction jets supplied by engine bleed. Aircraft performance is demonstrated in simulated STOVL maneuvers using a dynamic pilot model. The conclusion of this study is that propulsive lift control of aircraft pitch and roll is feasible and can provide as much as a 10 percent increase in engine lift rating over systems that employ reaction control alone. The dynamic response of practical propulsive lift configurations, however, is less than that of reaction control configurations, which must be offset through integration of the propulsion system and its control.

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Zong, Jianan, Bingjie Zhu, Zhongxi Hou, Xixiang Yang, and Jiaqi Zhai. "Evaluation and Comparison of Hybrid Wing VTOL UAV with Four Different Electric Propulsion Systems." Aerospace 8, no. 9 (September 9, 2021): 256. http://dx.doi.org/10.3390/aerospace8090256.

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Electric propulsion technology has attracted much attention in the aviation industry at present. It has the advantages of environmental protection, safety, low noise, and high design freedom. An important research branch of electric propulsion aircraft is electric vertical takeoff and landing (VTOL) aircraft, which is expected to play an important role in urban traffic in the future. Limited by battery energy density, all electric unmanned aerial vehicles (UAVs) are unable to meet the longer voyage. Series/parallel hybrid-electric propulsion and turboelectric propulsion are considered to be applied to VTOL UAVs to improve performances. In this paper, the potential of these four configurations of electric propulsion systems for small VTOL UAVs are evaluated and compared. The main purpose is to analyze the maximum takeoff mass and fuel consumption of VTOL UAVs with different propulsion systems that meet the same performance requirements and designed mission profiles. The differences and advantages of the four types propulsion VTOL UAV in the maximum takeoff mass and fuel consumption are obtained, which provides a basis for the design and configuration selection of VTOL UAV propulsion system.

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Piskin, Altug, Tolga Baklacioglu, and Onder Turan. "A hybrid ant colony–particle swarm optimization method (ACOPSO) for aerospace propulsion systems." Aircraft Engineering and Aerospace Technology 94, no. 5 (December 7, 2021): 687–93. http://dx.doi.org/10.1108/aeat-08-2021-0249.

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Purpose The purpose of this paper is to introduce a hybrid, metaheuristic, multimodal and multi-objective optimization tool that is needed for aerospace propulsion engineering problems. Design/methodology/approach Multi-objective hybrid optimization code is integrated with various benchmark and test functions that are selected suitable to the difficulty level of the aero propulsion performance problems. Findings Ant colony and particle swarm optimization (ACOPSO) has performed satisfactorily with benchmark problems. Research limitations/implications ACOPSO is able to solve multi-objective and multimodal problems. Because every optimization problem has specific features, it is necessary to search their general behavior using other algorithms. Practical implications In addition to the optimization solving, ACOPSO enables an alternative methodology for turbine engine performance calculations by using generic components maps. The user is flexible for searching various effects of component designs along with the compressor and turbine maps. Originality/value A hybrid optimization code that has not been used before is introduced. It is targeted use is propulsion systems optimization and design such as Turboshaft or turbofan by preparing the necessary engine functions. A number of input parameters and objective functions can be modified accordingly.

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Lorenz, Ralph. "Small satellites and electric propulsion - a review." Aeronautical Journal 95, no. 946 (July 1991): 204–13. http://dx.doi.org/10.1017/s0001924000023915.

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AbstractIn recent years, interest has grown in the use of small satellites for a variety of applications. In certain missions, where propulsion systems are necessary, electric propulsion technology can offer advantages. Small satellite technology and applications are reviewed and some of the features of various types of electric propulsion are discussed: missions where small satellites might use electric propulsion are described.

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Nathan, Stuart. "Polishing the Jewel in the Crown." Engineer 298, no. 7900 (July 2018): 28–29. http://dx.doi.org/10.12968/s0013-7758(23)90179-0.

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Jimenez, Darwin, Esteban Valencia, Ariel Herrera, Edgar Cando, and Marcelo Pozo. "Evaluation of Series and Parallel Hybrid Propulsion Systems for UAVs Implementing Distributed Propulsion Architectures." Aerospace 9, no. 2 (January 25, 2022): 63. http://dx.doi.org/10.3390/aerospace9020063.

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Current environmental policies for the aviation sector motivate the use of cleaner propulsion alternatives in order to reduce their CO2 footprint and noise pollution in the coming years. In this context, hybrid propulsion systems have emerged as a potential solution, as they have demonstrated a good trade-off between performance and low pollutant emissions. The present work carries out a comparison between parallel and series hybrid propulsion systems using heterogeneous and homogeneous distributed propulsion architectures. In order to highlight the opportunities of distributed propulsion systems and validate the methodology developed, a single propulsion hybrid configuration is used as baseline case for this study. For the propulsion system sizing, this work uses a parametric modelling tool, which includes a constraint analysis coupled with a weight estimation module to determine suitable configurations for a environmental monitoring mission. The latter module includes semi-empirical correlations to size the electric and mechanical components for each propulsion setup. From the results, it has been found that for the representative case of monitoring in the Galapagos Islands, which requires an endurance of approximate 7 h, the parallel hybrid system using three distributed propulsors presents the best performance features in terms of fuel savings, showing a 34% reduction compared with the baseline case. To summarize, the main contribution of this study lies on the development of a methodology to set potential hybrid distributed propulsion configurations for UAVs aimed for determined monitoring missions.

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O’Reilly, Dillon, Georg Herdrich, and Darren F. Kavanagh. "Electric Propulsion Methods for Small Satellites: A Review." Aerospace 8, no. 1 (January 18, 2021): 22. http://dx.doi.org/10.3390/aerospace8010022.

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Over 2500 active satellites are in orbit as of October 2020, with an increase of ~1000 smallsats in the past two years. Since 2012, over 1700 smallsats have been launched into orbit. It is projected that by 2025, there will be 1000 smallsats launched per year. Currently, these satellites do not have sufficient delta v capabilities for missions beyond Earth orbit. They are confined to their pre-selected orbit and in most cases, they cannot avoid collisions. Propulsion systems on smallsats provide orbital manoeuvring, station keeping, collision avoidance and safer de-orbit strategies. In return, this enables longer duration, higher functionality missions beyond Earth orbit. This article has reviewed electrostatic, electrothermal and electromagnetic propulsion methods based on state of the art research and the current knowledge base. Performance metrics by which these space propulsion systems can be evaluated are presented. The article outlines some of the existing limitations and shortcomings of current electric propulsion thruster systems and technologies. Moreover, the discussion contributes to the discourse by identifying potential research avenues to improve and advance electric propulsion systems for smallsats. The article has placed emphasis on space propulsion systems that are electric and enable interplanetary missions, while alternative approaches to propulsion have also received attention in the text, including light sails and nuclear electric propulsion amongst others.

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Misterek, Dean. "Book Review: Rocket Propulsion." AIAA Journal 57, no. 7 (July 2019): 3110. http://dx.doi.org/10.2514/1.j058612.

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Quarta, Alessandro, Giovanni Mengali, Marco Bassetto, and Lorenzo Niccolai. "Optimal Circle-to-Ellipse Orbit Transfer for Sun-Facing E-Sail." Aerospace 9, no. 11 (October 29, 2022): 671. http://dx.doi.org/10.3390/aerospace9110671.

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The transfer between two coplanar Keplerian orbits of a spacecraft with a continuous-thrust propulsion system is a classical problem of astrodynamics, in which a numerical procedure is usually employed to find the transfer trajectory that optimizes (i.e., maximizes or minimizes) a given performance index such as, for example, the delivered payload mass, the propellant mass, the total flight time, or a suitable combination of them. In the last decade, this class of problem has been thoroughly analyzed in the context of heliocentric mission scenarios of a spacecraft equipped with an Electric Solar Wind Sail as primary propulsion system. The aim of this paper is to further extend the existing related literature by analyzing the optimal transfer of an Electric Solar Wind Sail-based spacecraft with a Sun-facing attitude, a particular configuration in which the sail nominal plane is perpendicular to the Sun-spacecraft (i.e., radial) direction, so that the propulsion system is able to produce its maximum propulsive acceleration magnitude. The problem consists in transferring the spacecraft, which initially traces a heliocentric circular orbit, into an elliptic coplanar orbit of given eccentricity with a minimum-time trajectory. Using a classical indirect approach for trajectory optimization, the paper shows that a simplified version of the optimal control problem can be obtained by enforcing the typical transfer constraints. The numerical simulations show that the proposed approach is able to quantify the transfer performance in a parametric and general form, with a simple and efficient algorithm.

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Stalker, R. J., and A. Paull. "Experiments on cruise propulsion with a hydrogen scramjet." Aeronautical Journal 102, no. 1011 (January 1998): 37–44. http://dx.doi.org/10.1017/s0001924000065726.

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AbstractMeasurements of drag have been made, in a shock tunnel, on a simple integrated vehicle-engine combination for hypersonic cruise with hydrogen scramjet propulsion. The test flow Mach number was 6·4, and the velocity was 2·45 kms-1. Zero drag, which is the necessary condition for cruise, was achieved as the equivalence ratio approached one. It was found that an analysis using established aerodynamic concepts was adequate for predicting drag in the case of no combustion. When combustion occurred results of direct connect experiments provided a qualitative guide to the measured levels of drag, and indicated that thrust nozzle combustion was taking place. An heuristic analysis is used to point to the important effect this may have on propulsive lift.

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Walker, A. "Hybrid vehicle propulsion." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 217, no. 2 (February 1, 2003): 147–48. http://dx.doi.org/10.1177/095440700321700208.

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Dahms, Julius, and Andreas Bardenhagen. "Propulsion model for (hybrid) unmanned aircraft systems (UAS)." Aircraft Engineering and Aerospace Technology 91, no. 2 (February 4, 2019): 373–80. http://dx.doi.org/10.1108/aeat-01-2018-0033.

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Purpose This paper deals with the estimation of the necessary masses of propulsion components for multirotor UAS. Originally, within the design process of multirotors, this is an iterative problem, as the propulsion masses contribute to the total takeoff mass. Hence, they influence themselves and cannot be directly calculated. The paper aims to estimate the needed propulsion masses with respect to the requested thrust because of payload, airframe weight and drag forces and with respect to the requested flight time. Design/methodology/approach Analogue to the well-established design synthesis of airplanes, statistical data of existing electrical motors, propellers and rechargeable batteries are evaluated and analyzed. Applying Rankine and Froude’s momentum theory and a generic model for electro motor efficiency factors on the statistical performance data provides correlations between requested performance and, therefore, needed propulsion masses. These correlations are evaluated and analyzed in the scope of buoyant-vertical-thrusted hybrid UAS. Findings This paper provides a generic mathematical propulsion model. For given payloads, airframe structure weights and a requested flight time, appropriate motor, propeller and battery masses can be modelled that will provide appropriate thrust to lift payload, airframe and the propulsion unit itself over a requested flight time. Research limitations/implications The model takes into account a number of motors of four and is valid for the category of nano and small UAS. Practical implications The presented propulsion model enables a full numerical design process for vertical thrusted UAS. Hence, it is the precondition for design optimization and more efficient UAS. Originality/value The propulsion model is unique and it is valid for pure multirotor as well as for hybrid UAS too.

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Fioriti, Marco, Silvio Vaschetto, Sabrina Corpino, and Giovanna Premoli. "Design of hybrid electric heavy fuel MALE ISR UAV enabling technologies for military operations." Aircraft Engineering and Aerospace Technology 92, no. 5 (February 29, 2020): 745–55. http://dx.doi.org/10.1108/aeat-05-2019-0109.

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Purpose This paper aims to present the main results achieved in the frame of the TIVANO national-funded project which may anticipate, in a stepped approach, the evolution and the design of the enabling technologies needed for a hybrid/electric medium altitude long endurance (MALE) unmanned aerial vehicle (UAV) to perform persistent intelligence surveillance reconnaissance (ISR) military operations. Design/methodology/approach Different architectures of hybrid-propulsion system are analyzed pointing out their operating modes to select the more suitable architecture for the reference aircraft. The selected architecture is further analyzed together with its electric power plant branch focusing on electric system architecture and the selected electric machine. A final comparison between the hybrid and standard propulsion is given at aircraft level. Findings The use of hybrid propulsion may lead to a reduction of the total aircraft mass and an increase in safety level. However, this result comes together with a reduced performance in climb phase. Practical implications This study can be used as a reference for similar studies and it provides a detailed description of propulsion operating modes, power management, electric system and machine architecture. Originality/value This study presents a novel application of hybrid propulsion focusing on a three tons class MALE UAV for ISR missions. It provides new operating modes of the propulsion system and a detailed electric architecture of its powertrain branch and machine. Some considerations on noise emissions and infra-red traceability of this propulsion, at aircraft level.

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Weidner, J. P. "Hypersonic Propulsion-breaking the Thermal Barrier." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, no. 1 (January 1993): 47–59. http://dx.doi.org/10.1243/pime_proc_1993_207_246_02.

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The challenges of hypersonic propulsion impose unique features on the hypersonic vehicle—from large volume requirements to contain cryogenic fuel to airframe-integrated propulsion required to process sufficient quantities of air. Additional challenges exist in the design of the propulsion module that must be capable of efficiently processing air at very high enthalpies, adding and mixing fuel at supersonic speeds and expanding the exhaust products to generate thrust greater than drag. The paper explores the unique challenges of the integrated hypersonic propulsion system, addresses propulsion cycle selection to cope with the severe thermal environment and reviews the direction of propulsion research at hypervelocity speeds.

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Bore, C. L. "Some contributions to propulsion theory—The Stream Force Theorem and applications to propulsion." Aeronautical Journal 97, no. 964 (April 1993): 138–44. http://dx.doi.org/10.1017/s0001924000026026.

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SummaryAfter deriving the Stream Force Theorem, it is shown how this simplifies many problems of propulsion theory and makes the mathematics direct and concise. Applications discussed include forces upon ducting systems, intake entry losses, spill drag, mixing losses, errors in measuring intake losses by pitot traverse, and use of measured intake lip suction force in assessing entry losses and spill drag.

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Nosseir, Ahmed E. S., Angelo Cervone, and Angelo Pasini. "Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers." Aerospace 8, no. 1 (January 15, 2021): 20. http://dx.doi.org/10.3390/aerospace8010020.

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Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may require high-thrust impulsive capabilities. Thus, onboard primary and auxiliary propulsion systems capable of performing such orbital operations are required. Novelty in primary propulsion systems design calls for specific attention to miniaturization, which can be achieved, along the above-mentioned orbital transfer capabilities, by utilizing green monopropellants due to their relative high performance together with simplicity, and better storability when compared to gaseous and bi-propellants, especially for miniaturized systems. Owing to the ongoing rapid research activities in the green-propulsion field, it was necessary to extensively study and collect various data of green monopropellants properties and performance that would further assist analysts and designers in the research and development of liquid propulsion systems. This review traces the history and origins of green monopropellants and after intensive study of physicochemical properties of such propellants it was possible to classify green monopropellants to three main classes: Energetic Ionic Liquids (EILs), Liquid NOx Monopropellants, and Hydrogen Peroxide Aqueous Solutions (HPAS). Further, the tabulated data and performance comparisons will provide substantial assistance in using analysis tools—such as: Rocket Propulsion Analysis (RPA) and NASA CEA—for engineers and scientists dealing with chemical propulsion systems analysis and design. Some applications of green monopropellants were discussed through different propulsion systems configurations such as: multi-mode, dual mode, and combined chemical–electric propulsion. Although the in-space demonstrated EILs (i.e., AF-M315E and LMP-103S) are widely proposed and utilized in many space applications, the investigation transpired that NOx fuel blends possess the highest performance, while HPAS yield the lowest performance even compared to hydrazine.

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Souhair, Nabil, Mirko Magarotto, Raoul Andriulli, and Fabrizio Ponti. "Prediction of the Propulsive Performance of an Atmosphere-Breathing Electric Propulsion System on Cathode-Less Plasma Thruster." Aerospace 10, no. 2 (January 19, 2023): 100. http://dx.doi.org/10.3390/aerospace10020100.

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Atmosphere-breathing electric propulsion (ABEP) is a type of electric propulsion system that uses the atmosphere as a propellant source instead of a stored reservoir. This technology is still in its early stages, but holds the promise of providing a clean, efficient, and sustainable propulsion system for spacecraft, enabling very low Earth orbit (VLEO) mission scenarios. To optimise the ABEP technology, accurately simulating air-based plasma chemistry plays a crucial role. In this paper, an air-based global model (GM) is presented that includes a detailed chemistry model for the various reactions that are involved in ABEP applications. The model’s goal is to forecast the performance of a cathode-less RF plasma thruster under various pressure levels and species concentrations that are typical of VLEO missions. The GM was exploited to map the performance of a fictitious ABEP based on a cathode-less RF thruster in order to assess its feasibility in VLEO. The numerical model is promising as a tool for the design of ABEP systems and for the preliminary optimization of mission scenarios.

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Zong, Jianan, Bingjie Zhu, Zhongxi Hou, Xixiang Yang, and Jiaqi Zhai. "Sizing and Mission Profile Analysis of the Hybrid-Electric Propulsion System for Retrofitting a Fixed Wing VTOL Aircraft." International Journal of Aerospace Engineering 2022 (February 7, 2022): 1–10. http://dx.doi.org/10.1155/2022/9384931.

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Hybrid-electric technology can be expected to improve the performance of fixed wing vertical takeoff and landing (VTOL) aircraft. In this paper, we demonstrated a method of retrofitting a single-energy propulsion system prototype with a hybrid-electric propulsion system. Since the hybrid-electric system has several working modes, the optimal design results have strong coupling with mission performance. Therefore, we propose an analysis method of the mission profile to determine the design point. Finally, the payload-range sensitivity is studied. The results show that the hybrid-electric propulsion system can greatly increase the mission profile of aircraft. The analysis method of the mission profile also provides perspective for the hybrid-electric propulsion system design.

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Cinar, Gokcin, Elena Garcia, and Dimitri N. Mavris. "A framework for electrified propulsion architecture and operation analysis." Aircraft Engineering and Aerospace Technology 92, no. 5 (August 19, 2019): 675–84. http://dx.doi.org/10.1108/aeat-06-2019-0118.

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Purpose The purpose of this paper was to create a generic and flexible framework for the exploration, evaluation and side-by-side comparison of novel propulsion architectures. The intent for these evaluations was to account for varying operation strategies and to support architectural design space decisions, at the conceptual design stages, rather than single-point design solutions. Design/methodology/approach To this end, main propulsion subsystems were categorized into energy, power and thrust sources. Two types of matrices, namely, the property and interdependency matrices, were created to describe the relationships and power flows among these sources. These matrices were used to define various electrified propulsion architectures, including, but not limited to, turboelectric, series-parallel and distributed electric propulsion configurations. Findings As a case study, the matrices were used to generate and operate the distributed electric propulsion architecture of NASA’s X-57 Mod IV aircraft concept. The mission performance results were acceptably close to the data obtained from the literature. Finally, the matrices were used to simulate the changes in the operation strategy under two motor failure scenarios to demonstrate the ease of use, rapidness and automation. Originality/value It was seen that this new framework enables rapid and analysis-based comparisons among unconventional propulsion architectures where solutions are driven by requirements.

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Barkhoudarian, S., G. S. Cross, and Carl F. Lorenzo. "Advanced instrumentation for next-generation aerospace propulsion control systems." Journal of Propulsion and Power 12, no. 1 (January 1996): 205–6. http://dx.doi.org/10.2514/3.24012.

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Edwards, Tim. "Liquid Fuels and Propellants for Aerospace Propulsion: 1903-2003." Journal of Propulsion and Power 19, no. 6 (November 2003): 1089–107. http://dx.doi.org/10.2514/2.6946.

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Du, Yifan, Jinxing Zheng, Haiyang Liu, Yong Li, Cheng Zhou, Ge Wang, Zhuoyao Tang, Yudong Lu, and Luoqi Wang. "Theoretical Research on Magnetic Confinement Mechanism of Applied-Field Magnetoplasmadynamic Thruster." Aerospace 10, no. 2 (January 28, 2023): 124. http://dx.doi.org/10.3390/aerospace10020124.

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Since the invention of rockets, mankind has been constantly trying to explore the universe. It was not until the beginning of the last century that electric propulsion technology was introduced. With the same weight of fuel consumed as chemical propulsion, electric propulsion technology can transport a spacecraft to a more distant universe. With its excellent performance in terms of specific impulse and thrust, the MPDT (MagnetoPlasmaDynamic Thruster) is garnering significant attention in the field of electric propulsion. Recent research has focused on improving its propulsion performance and service life. Due to the complexity of its working mechanism, there is no perfect explanation for it. Further analysis of its working mechanism may lead to a solution to the improvement of certain significant performance aspects such as thrust. An ideal magnetic fluid model of the MPDT is established based on the MHD method, and the working mechanism is analyzed and summarized according to simulations and experiments. The results of the analysis indicate that reducing the size of the cathode could significantly improve the thruster’s performance.

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Kehayas, Nikolaos. "A LAMINAR FLOW, PROPULSIVE, JET-FLAPPED CONCEPT FOR ELECTRICALLY POWERED TRANSPORT AIRCRAFT." Aviation 27, no. 1 (February 23, 2023): 14–26. http://dx.doi.org/10.3846/aviation.2023.18498.

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Friction drag constitutes approximately half of the total drag of subsonic civil transport aircraft at cruise conditions. Several means were examined to control the flow over an aircraft and achieve laminar flow. Here, a new concept for friction drag reduction in the form of an integration of the aerodynamics and propulsion of the aircraft is put forward. Engines buried in the wing and at the rear of the fuselage suck the boundary layer of the entire wing and fuselage surface, and then, they used it as intake air and exhaust through ducts. At the wings, the engines exhaust in the form of a jet flap at the trailing edge providing distributed propulsion. By this laminar flow, propulsive concept laminar flow is established over the entire aircraft, resulting in substantial drag reduction. The analysis showed that out of the four electrically powered aircraft versions considered only the combined lift distribution with tailless fuselage is about to be feasible. It was also found that the example aircraft design is inappropriate. It is expected that a design purposely based on the proposed concept would bring electrically powered transport aircraft within the specific energy levels of present batteries.

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Girija, Athul Pradeepkumar, Sarag J. Saikia, and James M. Longuski. "Aerocapture: Enabling Small Spacecraft Direct Access to Low-Circular Orbits for Planetary Constellations." Aerospace 10, no. 3 (March 10, 2023): 271. http://dx.doi.org/10.3390/aerospace10030271.

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Small satellite constellations in multiple-inclination, low-circular orbits around Mars and Venus have the potential to perform a range of high-value science investigations within cost-constrained missions. A major challenge for small satellites is that they require large ΔV to enter low-circular orbits, which can drive up both spacecraft mass and cost. Compared to chemical propulsion, which requires large amounts of propellant, and electric propulsion, which requires large solar arrays and comes with long flight times, aerocapture enables direct access to low-circular orbits at Mars and Venus with minimal ΔV. The study shows how drag-modulation aerocapture, when combined with small B-plane targeting maneuvers, allows the delivery of multiple small satellites to various-inclination, low-circular orbits to establish a constellation. Preliminary cost estimates indicate that by reducing the required ΔV for orbit insertion, aerocapture can potentially reduce the cost of a small satellite going to a low-circular Mars orbit compared to propulsive insertion. The ability of low-cost spacecraft to enter planetary orbits will enable a new paradigm of interplanetary missions using small dedicated launch vehicles and planetary constellations at Mars and Venus.

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Flurchick, K., and R. D. Etters. "An atomic hydrogen propulsion system." AIAA Journal 23, no. 7 (July 1985): 981–82. http://dx.doi.org/10.2514/3.9025.

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Friedrich, C., and P. A. Robertson. "Hybrid-Electric Propulsion for Aircraft." Journal of Aircraft 52, no. 1 (January 2015): 176–89. http://dx.doi.org/10.2514/1.c032660.

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Detwiler, Andrew G., and Arthur Jackson. "Contrail Formation and Propulsion Efficiency." Journal of Aircraft 39, no. 4 (July 2002): 638–44. http://dx.doi.org/10.2514/2.2976.

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Roy, G. D. "Propulsion Combustion: Fuels to Emissions." AIAA Journal 37, no. 7 (July 1999): 902–4. http://dx.doi.org/10.2514/2.7542.

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Gal-Or, Β. "The Fundamentals of Vectored Propulsion." International Journal of Turbo and Jet Engines 6, no. 1 (January 1989): 1–16. http://dx.doi.org/10.1515/tjj.1989.6.1.1.

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Jansen, Ralph H., Cheryl L. Bowman, Sean Clarke, David Avanesian, Paula J. Dempsey, and Rodger W. Dyson. "NASA electrified aircraft propulsion efforts." Aircraft Engineering and Aerospace Technology 92, no. 5 (December 6, 2019): 667–73. http://dx.doi.org/10.1108/aeat-05-2019-0098.

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Purpose This paper aims to review national aeronautics and space administration (NASA’s) broad investments in electrified aircraft propulsion (EAP). NASA investments are guided by an assessment of potential market impacts, technical key performance parameters, and technology readiness attained through a combination of studies, enabling fundamental research and flight research. Design/methodology/approach The impact of EAP varies by market and NASA is considering three markets as follows: national/international, on-demand mobility and short-haul regional air transport. Technical advances in key areas have been made that indicate EAP is a viable technology. Flight research is underway to demonstrate integrated solutions and inform standards and certification processes. Findings A key finding is that sufficient technical advances in key areas have been made, which indicate EAP is a viable technology for aircraft. Significant progress has been made to reduce EAP adoption barriers and further work is needed to transition the technology to a commercial product and improve the technology, so it is applicable to large transonic aircraft. Practical implications Significant progress has been made to reduce EAP adoption barriers and further work is needed to transition the technology to a commercial product and improve the technology, so it is applicable to large transonic aircraft. Originality/value This paper will review the activities of the hybrid gas-electric subproject of the Advanced Air Transport Technology Project, the Revolutionary Vertical Lift Technology Project and the X-57 Flight Demonstration Project, and discuss the potential EAP benefits for commercial and military applications. This paper focuses on the vehicle-related activities, however, there are related NASA activities in air space management and vehicle autonomy activities, as well as a breakthrough technology project called the Convergent Aeronautics Solutions Project. The target audience is people interested in EAP.

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Journal articles on the topic 'Aerospace Engineering - Propulsion'

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